CN105637208A

CN105637208A - A nozzle arrangement for an engine

Info

Publication number: CN105637208A
Application number: CN201480057007.5A
Authority: CN
Inventors: 艾伦·邦德; 海伦·韦伯
Original assignee: Reaction Engines Ltd
Current assignee: Reaction Engines Ltd
Priority date: 2013-10-11
Filing date: 2014-10-10
Publication date: 2016-06-01
Also published as: GB2519156A; JP2016535830A; GB201318112D0; WO2015052471A1; EP3055543A1; US20150101337A1; RU2016111697A

Abstract

A nozzle arrangement for an engine that is operable in both an air-breathing mode, in which the engine combusts air taken in from atmosphere with hydrogen from a store thereof, and in a rocket mode, in which the engine combusts oxygen from a store thereof with hydrogen from the store thereof. The nozzle arrangement may include a rocket combustion chamber fluidly coupled by a rocket throat to a rocket nozzle. The rocket nozzle includes a first portion adjacent the rocket throat and a second portion remote from the rocket throat and axially moveable relative to the first portion between a rocket position in which they form a substantially contiguous rocket nozzle and an air-breathing position in which they overlap to define an annular throat therebetween. The nozzle arrangement may also include at least one air-breathing combustion chamber arranged to be fluidly coupled to the annular throat when the first and second portions of the nozzle are in the air-breathing position.

Description

Jet pipe arrangement for electromotor

The cross reference of related application

The application requires in the priority of number of patent application GB1318112.8 that on October 11st, 2013 submits in Britain and is hereby incorporated by reference according to 35U.S.C. �� 119 (a), and according to 35U.S.C. �� 120 and 365 require on June 5th, 2014 submit to and be combined in also by quoting this U.S. Patent Application No. 14/296,628 priority and earlier application day rights and interests.

Technical field

The present invention relates to a kind of for not only can by the jet pipe arrangement of air-breathing mode but also the electromotor that can run by rocket mode. In many embodiment, this electromotor is used for Single Stage To Orbit space shuttle. It is also contemplated that other are applied.

Background technology

The SABRE electromotor developed by reaction electromotor (ReactionEngines) company of Oxfordshire, Britain is the aircraft engine for the application of such as Single Stage To Orbit space shuttle provides power. This electromotor can run by rocket mode again by air-breathing mode. In low altitude area, electromotor runs with air-breathing mode. In this mode, the turbine that electromotor expands through turbo-compressor by making the gaseous helium of airborne bin contained in closed circuit drives the compressor of this turbo-compressor to run to compress suction atmospheric air. Compressed air mixes with the hydrogen from airborne storage of liquid hydrogen device, and produced mixture burns and is then discharged to provide thrust. In high altitude localities, electromotor runs with rocket mode. In this mode, replace suck atmospheric air, the oxygen from airborne liquid oxygen storage device is mixed and ignition mixture by electromotor with this hydrogen, then by discharge thrust is provided. Rocket mode does not use turbo-compressor.

Have problems and how burning and discharge are provided in each in the two pattern. A solution is each to provide combustor separately and jet pipe for air-breathing mode and rocket mode, and namely the first combustor and jet pipe are for air-breathing mode, and combustor separately and jet pipe are for rocket mode. But, this approach will bring obvious weight and resistance to electromotor, and this is undesirable.

Alternative route is to provide for the combustion chamber shared of the two operational mode and the jet pipe being associated. But, in order to provide thrust in rocket mode, it is necessary to make this combustor become rocket chamber and make oxygen and hydrogen burn in room and then expand and discharged by rocket nozzle. But, in air-breathing mode, such arrangement is not best for operation. Rocket chamber will necessarily for high pressure operating energy loss. As a result of which it is, when running with air-breathing mode, it may be necessary to the suction atmospheric air compression ratio of about 100:1. It should be appreciated that this high compression ratio makes there is high hydrogen fuel flow. As a result of which it is, more hydrogen must be carried compared with in other situations, thus causing weight to increase and performance reduction. Therefore, this solution is also undesirable.

Therefore, it is desirable to provide a kind of arrangement solving these shortcomings.

Summary of the invention

First aspect according to this disclosure, provide for not only can by a kind of jet pipe arrangement of air-breathing mode but also the electromotor that can run by rocket mode, in this air-breathing mode, this electromotor is by the hydrogen burning of the air sucked from air and a bin from this electromotor, in this rocket mode, this electromotor is by the oxygen from one bin and the hydrogen burning from its bin, this jet pipe arrangement includes: a rocket chamber, this rocket chamber is fluidly coupled to a rocket nozzle by a rocket throat, this rocket nozzle includes the Part I of this rocket throat contiguous and away from the Part II of this rocket throat, and this Part II can move between a rocket position and a suction location relative to this Part I, in this rocket position, this Part I and Part II form a substantially continuous rocket nozzle, in this suction location, this Part I and Part II are overlapping to limit an annular throat between which, this rocket nozzle farther includes at least one air-breathing combustor, this at least one air-breathing combustor is arranged to when Part I and the Part II of this jet pipe are fluidly coupled to this annular throat when being in this suction location.

By each providing combustor separately for this rocket mode and air-breathing mode but provide the jet pipe shared, while provide and can make rocket burning and air-breathing burning each optimized combustor separately, it is to avoid the obvious weight of the multiple jet pipe separately of offer and resistance shortcoming (it is sizable for providing the resistance cost to the extra jet pipe of at least some of atmospheric flight " invalid "). Additionally, by provide a kind of include the jet pipe of two parts, these parts can overlapping be that one solution easily allows (at least one) air-breathing combustor and rocket chamber to share same jet pipe to provide the annular throat for this air-breathing mode. It has also been found that when when this air-breathing mode, such annular throat promotes that (at least under some operating conditions) is along the attachment stream of the wall of jet pipe.

The Part I of this jet pipe can be the generally frustoconical part that larger diameter end portion is arranged in a sagittal plane. This Part II can be the generally frustoconical part that small diameter end portion is arranged in a sagittal plane. The small diameter end portion of this Part II can include the substantially cylindrical portion that the cervical region from this Part II substantially axially extends. When in this rocket position, the larger diameter end portion of this Part I can engage the cervical region of this Part II to form this substantially continuous rocket nozzle. This joint can be substantially sealed joint.

This rocket chamber can be fixed on the Part I of this jet pipe with this rocket throat or relative it is fixing.

This at least one air-breathing combustor can include multiple air-breathing combustor, and each air-breathing combustor is arranged to when Part I and the Part II of this jet pipe are fluidly coupled to this annular throat when being in this suction location. These air-breathing combustor may be about what this jet pipe was along the circumferential direction distributed. The Part I that these air-breathing combustor may be about this jet pipe is along the circumferential direction distributed. These air-breathing combustor can be distributed with the angular pitch of substantial constant. This at least one air-breathing combustor can be fixed on the Part I of this jet pipe or it is fixing relatively.

When the Part I of this jet pipe and Part II are in this suction location, this at least one air-breathing combustor can be fluidly coupled to annular throat by an annular gas collection portion, and this annular gas collection portion is fluidly coupled to this annular throat. This annular gas collection portion can around the Part I of this jet pipe. This annular gas collection portion can be fixed on the Part I of this jet pipe or it is fixing relatively. This annular gas collection portion can be arranged to when being in this suction location to provide to seal between an outer surface overlapping by the Part II of this jet pipe of one of this annular gas collection portion outlet and the Part I of this jet pipe engage. This annular gas collection portion can be arranged to engage the small diameter end portion of this Part II when being in this suction location so that the outlet in this annular gas collection portion engages with providing between an inner surface of the Part II of this jet pipe to seal. This annular gas collection portion can be arranged to engage the cylindrical part of the small diameter end portion of this Part II when being in this suction location so that the outlet in this annular gas collection portion engages with providing between an inner surface of the Part II of this jet pipe to seal. Can providing fluid-tight flexible connection part between the inner surface of this annular gas collection portion and the Part II of jet pipe, this fluid-tight flexible connection part can provide fluid-tight connection to also allow for relative movement between which simultaneously. This fluid-tight flexible connection part can include corrugated tube arrangement.

This at least one air-breathing combustor can include the single annular air-breathing combustor of the Part I around this jet pipe. This single air-breathing combustor can be fixed on the Part I of this jet pipe or it is fixing relatively. This single annular air-breathing combustor can be arranged to when being in this suction location to provide to seal between an outer surface overlapping by the Part II of this jet pipe of this one of air-breathing combustor outlet of single annular and the Part I of this jet pipe engage. This single annular air-breathing combustor can be arranged to engage the small diameter end portion of this Part II when being in this suction location to engage with providing between an inner surface of the Part II of this jet pipe to seal exporting of single annular air-breathing combustor. This single annular air-breathing combustor can be arranged to engage the cylindrical part of the small diameter end portion of this Part II when being in this suction location so that the outlet in this annular gas collection portion engages with providing between an inner surface of the Part II of this jet pipe to seal. Can providing fluid-tight flexible connection part between the inner surface of this at least one air-breathing combustor and the Part II of this jet pipe, this fluid-tight flexible connection part can provide fluid-tight connection to also allow for relative movement between which simultaneously. This fluid-tight flexible connection part can include corrugated tube arrangement.

This at least one air-breathing combustor can be arranged to receive compressed atmospheric air and the hydrogen from its bin. This rocket chamber can be arranged to receive the oxygen each from its corresponding bin and hydrogen.

The geometry of this jet pipe may be such that when when this air-breathing mode, there is diversity in this annular throat between overlapping Part I and the Part II of this jet pipe.

What have been found that this annular throat disperses the heat transfer characteristic that causes in the region of this annular throat more preferably. In particular, it was found that heat transmission capacity in the region is less than the heat transmission capacity for other annular throat geometries.

Dispersing of this annular throat may be such that this throat radial width in its exit and this throat ratio in the radial width of its porch is more than 1:1 and less than 4:1. This ratio can be greater than 1:1 and less than 3.5:1. This ratio can be between 1.5:1 and 3.5:1. This throat can be defined as the overlapping region between the Part II of this jet pipe and Part I, correspondingly defines the position of this entrance and exit.

The outlet of the area ratio of the Part I of this jet pipe, i.e. this Part I and the ratio of this rocket throat can be between 20:1 and 50:1. This ratio can be between 25:1 and 35:1. In an embodiment, this ratio can be 30:1.

The outlet of the area ratio of substantially continuous rocket nozzle that formed in this rocket mode, i.e. this Part II and the ratio of this rocket throat can be at least 100:1, in order to realize desired exhaust velocity. This ratio can be between 110:1 and 130:1. In an embodiment, this ratio can be 120:1.

This jet pipe arrangement can include an actuator arrangement, and this actuator arrangement is arranged to move between these two positions the Part II of this jet pipe. This actuator arrangement can include at least one electromechanical actuator and/or at least one electro-hydraulic actuator.

Second aspect according to this disclosure, provide a kind of not only can by air-breathing mode but also the electromotor that can run by rocket mode, in this air-breathing mode, this electromotor is by the hydrogen burning of the air sucked from air and a bin from this electromotor, in this rocket mode, this electromotor is by the oxygen from one bin and the hydrogen burning from its bin, this electromotor includes multiple jet pipe arrangement, these jet pipes each include: a rocket chamber, this rocket chamber is fluidly coupled to a rocket nozzle by a rocket throat, this rocket nozzle includes the Part I of this throat contiguous and away from the Part II of this throat, and this Part II can move between a rocket position and a suction location relative to this Part I, in this rocket position, this Part I and Part II form a substantially continuous rocket nozzle, in this suction location, this Part I and Part II are overlapping to limit an annular throat between which, this rocket nozzle farther includes at least one air-breathing combustor, this at least one air-breathing combustor is arranged to when Part I and the Part II of this jet pipe are fluidly coupled to this annular throat when being in this suction location.

Multiple optional feature of this first aspect are also the optional feature of this second aspect.

Brief Description Of Drawings

Fig. 1 illustrates the perspective view that four jet pipes arrange;

Fig. 2 illustrates representative jet pipe arrangement when these jet pipe arrangements are in air-breathing operational mode; And

Fig. 3 illustrates representative jet pipe arrangement when these jet pipe arrangements are in rocket operational mode.

Describe in detail

Fig. 1 illustrates a part for electromotor. A kind of application of this electromotor would is that and provides power to Single Stage To Orbit space shuttle. This electromotor can run by both of which: air-breathing mode, sucks air from air in this mode and uses turbo-compressor to burn for the liquid hydrogen with airborne bin to compress air; And rocket mode, do not have air to be inhaled in this mode and instead hydrogen burns with the oxygen from airborne bin.

With continued reference to Fig. 1, it is shown that four jet pipes arrange 10. These jet pipe arrangements are shown as spatially being arranged to them generally in this electromotor, and these jet pipe arrangements form a part for this electromotor. These four jet pipe arrangements 10 are to arrange in the way of the compactest: two take advantage of two arrangements, so that the axis that each jet pipe arranges is through same foursquare corresponding turning. Also show the miscellaneous part of electromotor, such as when providing thrust, these jet pipes arrange 10 retroactions against its primary structural member 20.

Each jet pipe arrangement 10 has several parts. For each jet pipe arrangement, rocket chamber 32 is connected to and is fluidly coupled to rocket throat 33, and this rocket throat is connected to and is fluidly coupled to rocket nozzle 35. Rocket nozzle 35 is in two parts: the first nozzle portion 30, and this first nozzle portion is close to and is connected to rocket throat 33; And second nozzle portion 40, the contiguous Part I 30 of this second nozzle portion but be what to be separated with this part. As understood from the following description, the two part 30,40 of jet pipe 35 can relative to each other move between the two positions. In a position that will be referred to as " rocket position ", what the two part 30,40 was positioned such that them is internally formed continuous print rocket nozzle. This position is to use during the rocket operational mode of this electromotor. To be referred to as in the position of " suction location " at another, Part II 40 is axially moved into partly overlapping with the larger diameter end portion of Part I 30 relative to the remainder of this electromotor. This position is to use during the air-breathing operational mode of this electromotor, and is the arrangement shown in Fig. 1. The two position is further illustrated below with reference to Fig. 2 and Fig. 3.

With continued reference to Fig. 1, each jet pipe arrangement 10 farther includes three air-breathing combustor 42. These air-breathing combustor are around what the Part I of jet pipe 35 arranged with constant angle pitch. Each air-breathing combustor 42 is connected to the annular manifold of 41 forms in gas collection portion (plenum) and in flow communication. Gas collection portion 41 extends around the Part I 30 of jet pipe 40 and is installed on Part I 30.

Fig. 2 illustrates in greater detail this arrangement. The figure shows representative jet pipe when these jet pipes 10 are in this air-breathing mode, in this air-breathing mode, the Part II 40 of jet pipe 10 is in suction location, it can be seen that this Part II and Part I 30 and be that the larger diameter end portion with this part 30 partly overlaps in this suction location. As can be seen, the exhaust manifold of these three air-breathing combustor 42 is formed with the gas collection portion 41 shown in cross section.

The Part I of jet pipe 10 and Part II are each generally Frusto-conical. But, the small diameter end portion of the Part II 40 of jet pipe 10 additionally includes cylindrical section 43, and this cylinder section is coaxial with the remainder of jet pipe 10. When Part II 40 is in this position, this cylinder section makes this cylinder section engage in the way of substantially sealed with the outer radial periphery edge in gas collection portion 41. The outer surface of the Part I 30 of jet pipe 10 has shoulder portion 34, and this shoulder portion engages in the way of substantially sealed with the radially inner circumference edge in gas collection portion 41. Because the Part I 30 of jet pipe 10 does not move relative to gas collection portion 41 (or actually described except Part II 40 every other parts), so this is bonded in running is permanent. The cylindrical inner side of section 43 together provides the annularly flow path connected that flows with gas collection portion 41 of a cross section substantial constant with the outside of shoulder portion 34. In alternative embodiments, this cylinder section is formed without a part for Part II 40, and is attached in gas collection portion 41 and is formed the part in this gas collection portion. It should be appreciated that it practice, this is to provide the alternative of identical result.

Overlap between the two part 30,40 of jet pipe 10 creates annular throat 50 around the inner side in the outside of the larger diameter end portion of the first nozzle portion 30 and the small diameter end portion of the second nozzle portion 40. Annularly flow path configured in fluid communication between annular throat 50 and cylindrical section 43 and shoulder portion 34. Although being made that omission from Fig. 2 and Fig. 3 for simplifying diagram purpose, but the geometry of the Part I 30 of jet pipe 10 and Part II 40 being so that annular throat 50 is dispersed. In other words, the area of section of this annular throat increases along axis away from these combustor 42. What have been found that this annular throat disperses the heat transfer characteristic that causes in the region of this annular throat more preferably. In particular, it was found that the heat transmission in this region is the form of the fiaring cone of the inlet port in this annular throat contiguous, the axial length of this fiaring cone annularly throat 50 does not extend far. This is compared with the annular throat with more constant cross-sectional area, it has been found that, in the annular throat of more constant cross-sectional area, heat transmission is high along much bigger axial length. Therefore, if this annular throat is designed to have disperses geometry, it is easier to ensure the effective cooling in this annular throat region. It should be appreciated that in the present embodiment, being effectively cooled in the design of jet pipe arrangement is very important Consideration, because it can greatly affect the safety of this arrangement, maintenance cost and service life.

Fig. 3 illustrates representative jet pipe when these jet pipes 10 are in rocket mode. In this mode, second nozzle portion 40 is positioned in this rocket position. In this position, relative to internal nozzle part 30, the second nozzle portion 40 is located so that annular throat 50 is Guan Bi. In other words, in figure 3, the second nozzle portion 40 relative to the first nozzle portion 30 by right translation. The generally frustoconical section so making the two nozzle portion 30,40 is no longer overlapping, but can be formed and be shaped like in the rocket nozzle (it should be understood that the cylindrical section 43 of Part II 40 is still overlapping with Part I 30) dispersed continuously of conventional rocket nozzle.

In Proof of Concept modeling process, multiple different geometry having been modeled, the cold flow properties of generation illustrates in Table 1. In the table, AR is the outlet area ratio with rocket throat 33 of the Part I 30 of jet pipe 10, and E is the area of section ratio (ratio E is preferably more than 1:1 and less than 4:1) with the area of section of annular throat 50 of annular flow passage outlet 35. These row illustrate the result for the jet pipe with different E values and AR value. These row illustrate for these different jet pipes result under the different atmospheric pressures corresponding from different operation height above sea levels. Letter in these cells has following implication:

First letter:

A: adhere to stream completely

S: separate stream

Second letter:

O: wake flow (wake) keeps open

C: wake flow is closed

Trigram:

S: there is recompression (namely impacting) along wall

N: without impacting

Table 1: cold flow properties

It is shown that these are for make AR and the E that minimizing separation is desirably higher, and

And (as described elsewhere in this disclosure) makes E more than 1, so that there is dispersing of this annular throat and heat transfer characteristic can be improved. It is contemplated that in other embodiments, it is possible to use any geometry illustrated in Table 1. Therefore it is proposed to, AR can be in the scope of 20 to 50. But, because making area ratio may result in, more than about 30:1, the engineering problem that Part II 40 to jet pipe 10 is relevant relative to the amount of recovery required for Part I 30, in the present embodiment, have selected the area ratio of 30:1.

In this embodiment, the total area ratio of this rocket nozzle, the outlet of Part II 40 are selected as 120:1 with the area ratio of rocket throat 33. Again, in other embodiments other ratios be it is contemplated that and be possible. For example, it is contemplated that arrive the ratio of at least 100:1.

In this embodiment, E is selected as 2.0. Again, in other embodiments other values of E be it is contemplated that and be possible. For example, it is envisioned that, E is in the scope of 1 to 3.5 or 1 to 4.

In running, and with reference to Fig. 2, this electromotor generally starts to take off and continue to run in this mode at relatively low height above sea level run duration with air-breathing mode. Compressed atmospheric air is transported in each of these three air-breathing combustor 42, and in these air-breathing combustor, this atmospheric air mixes with the hydrogen from airborne bin and burns. Combustion product flows to annular gas collection portion 41 from combustor 42, and flows to annular throat 50 from the annular gas collection portion 41 between cylindrical section 43 and shoulder portion 34. The axial length of these combustion products annularly throat 50 expands to some extent and leads to from this annular throat the remainder of Part II 40 of jet pipe 10, leaves part 40 afterwards and leaves jet pipe 10 together. It has also been found that when when this air-breathing mode, annular throat promotes that (at least under some operating conditions) is along the attachment stream of the wall of jet pipe. Might not be all this situation for all operation height above sea levels, but it is equivalent to another benefit of this annular throat, regardless of whether this annular throat is dispersed. Correspondingly, in certain embodiments, annular throat then can not be dispersed and can be other geometries.

With reference to Fig. 3, at the High aititude At The Height that air weakens, this electromotor is transformed into rocket operational mode. This relates to multiple actuator (not shown), operates these actuators axially to be moved in rocket position by the Part II 40 of jet pipe 10. In this configuration, from air, do not suck air; On the contrary, originate from the oxygen of airborne bin and from the hydrogen of airborne bin mixed combining combustion in a usual manner in rocket chamber 32, combustion product now actually in continuous print routine rocket nozzle experience expand and be discharged.

As already mentioned above, by each providing combustor separately for this rocket mode and air-breathing mode but provide the jet pipe shared, while provide and can make rocket burning and air-breathing burning each optimized combustor separately, it is to avoid the obvious weight of the multiple jet pipe separately of offer and resistance shortcoming (it is sizable for providing the resistance cost to the extra jet pipe of at least some of atmospheric flight " invalid "). Further it is provided that a kind of include the jet pipe of two parts, these parts can overlapping be that a kind of solution easily is to allow these air-breathing combustor and rocket chamber to share same jet pipe to provide the annular throat for this air-breathing mode.

Claims

1. for not only can by a kind of jet pipe arrangement of air-breathing mode but also the electromotor that can run by rocket mode, in this air-breathing mode, this electromotor is by the hydrogen burning of the air sucked from air and a bin from this electromotor, in this rocket mode, this electromotor is by the oxygen from one bin and the hydrogen burning from its bin, and this jet pipe arrangement includes:

One rocket nozzle;

One rocket chamber, this rocket chamber is fluidly coupled to this rocket nozzle by a rocket throat, this rocket nozzle includes the Part I of this rocket throat contiguous and away from the Part II of this rocket throat, and this Part II can move between a rocket position and a suction location relative to this Part I, in this rocket position, this Part I and Part II form a substantially continuous rocket nozzle, in this suction location, this Part I and Part II are overlapping to limit an annular throat between which, wherein, the Part I of this rocket nozzle is that larger diameter end portion is arranged in a generally frustoconical part of a sagittal plane and this Part II is the generally frustoconical part that small diameter end portion is arranged in a sagittal plane, the small diameter end portion of this Part II includes the substantially cylindrical portion that the cervical region from this Part II substantially axially extends, and when in this rocket position, the larger diameter end portion of this Part I engages the cervical region of this Part II to form this substantially continuous rocket nozzle in the way of substantially sealed joint, and

At least one air-breathing combustor, this at least one air-breathing combustor is arranged to when Part I and the Part II of this rocket nozzle are fluidly coupled to this annular throat when being in this suction location.

2. jet pipe arrangement according to claim 1, wherein, this at least one air-breathing combustor includes multiple air-breathing combustor, and each air-breathing combustor is arranged to when Part I and the Part II of this jet pipe are fluidly coupled to this annular throat when being in this suction location.

3. jet pipe arrangement according to claim 1 and 2, wherein, these air-breathing combustor are around what this jet pipe was along the circumferential direction distributed.

4. jet pipe arrangement according to claim 3, wherein, the Part I that these air-breathing combustor are around this jet pipe is along the circumferential direction distributed.

5. the jet pipe arrangement according to any one of the preceding claims, wherein, this at least one air-breathing combustor is fixed on the Part I of this jet pipe or it is fixing relatively.

6. the jet pipe arrangement according to any one of the preceding claims, wherein, when the Part I of this jet pipe and Part II are in this suction location, this at least one air-breathing combustor is fluidly coupled to this annular throat by an annular gas collection portion, and this annular gas collection portion is fluidly coupled to this annular throat.

7. jet pipe arrangement according to claim 6, wherein, this annular gas collection portion is around the Part I of this jet pipe.

8. the jet pipe arrangement according to claim 6 or 7, wherein, this annular gas collection portion is fixed on the Part I of this jet pipe or it is fixing relatively.

9. the jet pipe arrangement according to any one of claim 6 to 8, wherein, this annular gas collection portion is arranged to when being in this suction location to provide to seal between an outer surface overlapping by the Part II of this jet pipe of one of this annular gas collection portion outlet and the Part I of this jet pipe engage.

10. the jet pipe arrangement according to any one of claim 6 to 9, wherein, this annular gas collection portion is arranged to engage the small diameter end portion of this Part II when being in this suction location so that the outlet in this annular gas collection portion engages with providing between an inner surface of the Part II of this jet pipe to seal.

11. the jet pipe arrangement according to any one of claim 6 to 10, wherein, the small diameter end portion of the Part II of this nozzle includes the substantially cylindrical portion that the cervical region from this Part II substantially axially extends, and this annular gas collection portion is arranged to engage this cylindrical part so that the outlet in this annular gas collection portion engages with providing between an inner surface of the Part II of this jet pipe to seal when being in this suction location.

12. the jet pipe arrangement according to any one of claim 1 to 5, wherein, this at least one air-breathing combustor includes the single annular air-breathing combustor of the Part I around this jet pipe.

13. jet pipe arrangement according to claim 12, wherein, this single annular air-breathing combustor is fixed on the Part I of this jet pipe or it is fixing relatively.

14. the jet pipe arrangement according to any one of claim 6 to 8, wherein, this single annular air-breathing combustor is arranged to when being in this suction location to provide to seal between an outer surface overlapping by the Part II of this jet pipe of this one of air-breathing combustor outlet of single annular and the Part I of this jet pipe engage.

15. the jet pipe arrangement according to any one of claim 6 to 9, wherein, this single annular air-breathing combustor is arranged to engage the small diameter end portion of this Part II when being in this suction location to engage with providing between an inner surface of the Part II of this jet pipe to seal exporting of single annular air-breathing combustor.

16. the jet pipe arrangement according to any one of claim 6 to 10, wherein, the small diameter end portion of the Part II of this nozzle includes the substantially cylindrical portion that the cervical region from this Part II substantially axially extends, and this single annular air-breathing combustor is arranged to engage this cylindrical part to engage with providing between an inner surface of the Part II of this jet pipe to seal exporting of this single annular air-breathing combustor when being in this suction location.

17. the jet pipe arrangement according to any one of the preceding claims, wherein, in this air-breathing mode, there is diversity in the circular passage between overlapping Part I and the Part II of this jet pipe.

18. jet pipe arrangement according to claim 17, wherein, the ratio of the area of section dispersing the area of section so that the outlet of this annular flow passage and this annular throat of this circular passage is more than 1:1 and less than 4:1.

19. the jet pipe arrangement according to any one of the preceding claims, farther including an actuator arrangement, this actuator arrangement is arranged to move between these two positions the Part II of this jet pipe.

20. one kind not only can by air-breathing mode but also the electromotor that can run by rocket mode, in this air-breathing mode, this electromotor is by the hydrogen burning of the air sucked from air and a bin from this electromotor, in this rocket mode, this electromotor is by the oxygen from one bin and the hydrogen burning from its bin, and this electromotor includes respective multiple jet pipe arrangements according to any one of claim 1 to 19.

21. one kind substantially such as the jet pipe arrangement that is described with reference to the accompanying figures at this.